Hostname: page-component-586b7cd67f-dlnhk Total loading time: 0 Render date: 2024-11-23T22:18:32.356Z Has data issue: false hasContentIssue false
  • English
  • Français

Some Practical Aspects of Compressor Blade Vibration*

Published online by Cambridge University Press:  04 July 2016

E. K. Armstrong  and
R. E. Stevenson
E. K. Armstrong
Affiliation:
Bristol Siddeley Engines Ltd.
R. E. Stevenson
Affiliation:
Bristol Siddeley Engines Ltd.
Get access Rights & Permissions [Opens in a new window]

Extract

The object of this paper is to set down an overall picture of the practical aspects of compressor blade vibration. In doing so it is inevitable that a certain content is effectively a repeat of other people's contributions to the subject. The authors make no apology for this and offer the paper as a "state of the art" as practised at Bristol Siddeley Engines Ltd. In bringing together the many relevant issues of this problem, it is hoped that a useful presentation is obtained.

There is little hesitation in indicating the most obvious and important practical aspect of blade vibration as that of the inherent danger of blade failure and it is known that the axial flow compressor is susceptible to complete failure caused by the fatigue of one blade.

The multi-stage axial flow compressor is a highly complex aerodynamic machine with, its early and late stages required to operate over wide ranges of incidence and Mach number conditions. To some extent, of course, use of variable geometry can reduce this to less taxing proportions. The aerodynamic environment of front stages has broad boundaries somewhat wider than those relating to rear stages, while middle blade rows generally operate under sensibly constant conditions. This diminishing “severity” of operation, front, rear to middle stage blading is not unrelated to the incidence of blade vibration problems which shows a similar pattern.

Type
Research Article
Information
The Aeronautical Journal , Volume 64 , Issue 591 , March 1960 , pp. 117 - 130
Copyright
Copyright © Royal Aeronautical Society 1960

Access options

Get access to the full version of this content by using one of the access options below. (Log in options will check for institutional or personal access. Content may require purchase if you do not have access.)

Footnotes

*

The 1133rd lecture to be given before the Society —on 8th December 1959.

References

1.Shannon, J. F. (1945). Vibration Problems in Gas Turbines, Centrifugal and Axial-Flow Compressors. R. & M. 2226, 1945.Google Scholar
2.Pearson, H. (1953). The Aerodynamics of Compressor Blade Vibration.Fourth Anglo-American Aeronautical Conference, London. The Royal Aeronautical Society, 1953.Google Scholar
3.Sisto, F. (1953). Stall Flutter in Cascades. Journal of the Aeronautical Sciences, Vol. 20, No. 9, p. 598, 1953.CrossRefGoogle Scholar
4.Carter, A. D. S. and Kilpatrick, D. A. (1957). Self- Excited Vibration of Axial Flow Compressor Blades. Proc. I. Mech. E., Vol. 171, No. 7, p. 245, 1957.CrossRefGoogle Scholar
5.Schnittger, J. R. (1957). Communication to Discussion on Carter's and Kilpatrick's Paper. (Ref. 4). 1957.Google Scholar
6.Miner, M. A. (1945). Cumulative Damage in Fatigue. Journal of Applied Mechanics, Vol. 12, p. A159, 1945.CrossRefGoogle Scholar